N499MC
Registered owner: ATLAS AIR INC, NY (owner ≠ operator)
Operators of this aircraft
Who operated this tail, and how firmly we know it.
| Operator | Role | Period | Basis |
|---|---|---|---|
| ATLAS AIR INC (UIEA) | Operator | 2010-12-04 – 2010-12-04 | Operator named in NTSB report |
| ATLAS AIR INC | Operator | 2010-12-04 – 2010-12-04 | Operator named in NTSB report |
Accident & incident history
Maintenance disclosures
EQUIPMENT COOLING EICAS MESSAGE IN FLIGHT. REPLACED FLIGHT DECK LOW FLOW DETECTOR & OPS CHECKED GOOD IAW AMM 21-58-02/201. REMOVED AND REPLACED FLIGHT DECK FLOW REGULATOR VALVE & OPS CHECKED GOOD IAW AMM 21-61-09/501. DURING TROUBLESHOOTING, FOUND FOD INSIDE COOLING DUCT. FOD REMOVED. FOUND FWD E/E COOLING FAN BOOT CLAMP LEAKING AIR. RESECURED CLAMP & LEAK CHECKED GOOD IAW AMM 21-58-01. PERFORMED GROUND TEST OF E/E COOLING SYSTEM & OPS CHECKED GOOD IAW AMM 21-58-02/201.
1EA CRACK WAS FOUND ON LH STA 1000 LBL 11.33 FRONT SPAR INTERCOSTAL LUG FITTING.(<P>FITTING REPLACEMENT CARRIED OUT AS PER ATLAS AIR EO: 4453C024 REV 4 PART 3 STEP 3. NO FURTHER DEFECTS NOTED.</P>)
LHW I/B MID FLAP FAIRING EXTERIOR SURFACE FOUND DENT.(<P>PERFORMED REPAIR AT DENT AREA AS PER SRM 51-70-07 PAR 5.A.(1) REV 103. NO FURTHER DEFECTS NOTED.</P>)
COCKPIT - CTR CONSOLE RH FWD VERTICAL METAL PANEL LWR CORNER NEAR I/B RUDDER PADAL FOUND CRACK.(<P>PANEL CRACK AREA REPAIRED AS PER RI-25-10-17662 REV A. NO FURTHER DEFECTS NOTED.</P>)
COCKPIT CTR CONSOLE LH FWD VERTICAL METAL PNL LWR CORNER NEAR I/B RUDDER PEDAL FOUND CRACK.(<P>PANEL CRACK AREA REPAIRED AS PER RI-25-10-17662 REV A. NO FURTHER DEFECTS NOTED.</P>)
LHW O/B MID FLAP FOUND BOLT HOLE ELONGATED.(<P>PERFORMED REPAIR AT ELONGATED BOLT HOLE AS PER SRM 51-70-07 PAR 5.K REV 103. NO FURTHER DEFECTS NOTED.</P>)
RHW O/B MID FLAP FOUND BOLT HOLE ELONGATED.(<P>PERFORMED REPAIR AT ELONGATED BOLT HOLE AS PER SRM 51-70-07 PAR 5.K REV 103. NO FURTHER DEFECTS NOTED.</P>)
#4 ENG O/B T/REV INNER WALL FOUND DELAMINATED AT FWD 3 O'CLOCK POSITION(<P>DELAMINATE AREA REPAIRED AS PER ATLAS AIR EA-1978A219 REV O FIG 2. NO FURTHER DEFECTS NOTED.</P>)
1 EA CRACK WAS FOUND ON RH BS 1480 LONGERON EXTENSION FITTING RADIUS AREA.(<P>LONGERON EXTENSION FITTING MOD CARRIED OUT AS PER ATLAS AIR EO NO: 4453A818 REV 20 PART 8. NO FURTHER DEFECTS NOTED.</P>)
1 EA CRACK WAS FOUND AT FASTENER HOLE 6 O'CLOCK POSITION AT RH BS 1480 B/HEAD FRAME WEB I/B UPPER AREA. FRAME WEB REPAIRED AS PER ATLAS AIR EO 4453A818 REV 20 PART 8. NO FURTHER DEFECTS NOTED.
NOSE CARGO DOOR (P/N: 65B13016-10, S/N: 000123) BIRD STRIKE DAMAGE STA 140 AND STA 200, BETWEEN S31R AND S42AR NOSE CARGO DOOR SKIN, FRAMES AND STRINGERS - CAT B PERMANENT REPAIRS.(<P>NOSE CARGO DOOR SKIN DENT #1 AND DENT #2 REPAIRED AS PER RI-52-30-17671 REV A. NO FURTHER DEFECTS NOTED.</P>)
NOSE CARGO DOOR BIRD STRIKE DAMAGE REPETITION INSPECTION FINDING STA 160 STR 36R, FOUND DENT. STRINGER REPAIRED AS PER RI-52-30-17671 REV A. NO FURTHER DEFECTS NOTED.</P>)
NOSE CARGO DOOR BIRD STRIKE DAMAGE REPETITION INSPECTION FINDING STA 180 BTN STR 31AR AND STA 34R. DOUBLER FOUND TOOL MARK. FRAME TOOL MARK AREA REPAIRED AS PER RI-52-30-17671 REV A. NO FURTHER DEFECTS NOTED.
LH BLG I/B W/W DOOR CHAFE PLATE FOUND CRACK.(<P>LH BLG I/B W/W DOOR CHAFE PLATE REPLACE AS PER HX RI-32-14-17675 REV A. NO FURTHER DEFECTS NOTED.</P>)
1EA CRACK WAS FOUND ON RH STA 1000 RBL 11.33 FRONT SPAR INTERCOSTAL LUG FITTING.(<P>FITTING REPLACEMENT CARRIED OUT AS PER ATLAS AIR EO: 4453C024 REV 4 PART 7 STEP 3. NO FURTHER DEFECTS NOTED.</P>)
LHW O/B MID FLAP FOUND BOLT HOLE ELONGATED.(<P>PERFORMED REPAIR AT ELONGATED BOLT HOLE AS PER SRM 51-70-07 PAR 5.K REV 103. NO FURTHER DEFECTS NOTED.</P>)
RHW I/B FORE FLAP EXTERIOR SURFACE FOUND DELAMINATED.(<P>PERFORMED REPAIR AT DELAMINATED AREA AS PER SRM 51-70-07 PAR 5A.(1) REV 103. NO FURTHER DEFECTS NOTED.</P>)
LHW I/B FORE FLAP EXTERIOR SURFACE FOUND DELAMINATED.(<P>PERFORMED REPAIR AT DELAMINATED AREA AS PER SRM 51-70-07 PAR 5.A.(1) REV 103. NO FURTHER DEFECTS NOTED.</P>)
LHW I/B FORE FLAP EXTERIOR SURFACE FOUND DELAMINATED.(<P>PERFORMED REPAIR AT DELAMINATED AREA AS PER SRM 51-70-07 PAR 5.A.(1) REV 103. NO FURTHER DEFECTS NOTED.</P>)
LHW I/B FORE FLAP EXTERIOR SURFACE FOUND DELAMINATED.(<P>PERFORMED REPAIR AT DELAMINATED AREA AS PER SRM 51-70-07 PAR 5.A.(1) REV 103. NO FURTHER DEFECTS NOTED.</P>)
CORROSION ON SEAT TRACK/FLOOR BEAM AT RBL 11.33 AT STA 1900.(<P>REPLACED 2 SECTIONS OF SEAT TRACKS FROM PREVIOUS REPAIR STA 1610 TO STA 1766.5 TO FACTORY SPLICE AND 2ND SECTION FROM STA 1766-.5 TO STA. 1910 TO PREVIOUS REPAIR SPLICE RBL 11.33 PER B747-400F SRM 53-00-52-2R-12 REPAIR 12 REV 102. REF > HM627-20061 FOR REPAIR.&NBSP;&NBSP;NO FURTHER DEFECTS NOTED.</P>)
CORROSION ON SEAT TRACK/FLOOR BEAM AT RBL 11.33 STA. 1820.(<P>REPLACED 2 EACH SECTIONS OF SEAT TRACKS FROM PREVIOUS REPAIR STA. 1610-1766.5 TO FACTORY SPLICE AND 2ND SECTON FROM STA. 1766.5 TO STA. 1910 TO PREVIOUS REPAIR SPLICE RBL 11.33 PER B747-400F SRM 53-00-52-2R-12 REP 12 REV 102. REF > HM627-20061 FOR REPLACEMENT. NO FURTHER DEFECTS NOTED</P>)
CORROSION ON SEAT TRACK/FLOOR BEAM AT LBL 11.33 AT STA. 1620,<BR>(<P>REPAIRED SEAT TRACK FROM STA 1590-1650 LBL PER B747-400 SRM 53-00-52-2R-12 REPAIR 12. NO FURTHER DEFECTS NOTED</P>)
CORROSION FOUND ON FLANGE ON RH SIDE BODY LANDING GEAR BEARING FITTING CAP.(<P STYLE="MARGIN: 0IN; MARGIN-BOTTOM: .0001PT;">REMOVED AND REPLACED RH SIDE BODY LANDING GEAR BEARING FITTING CAP PER B747 AMM 32-13-01-004-001 AND 32-13-01-404-022. SRM 53-40-90-2R-1 REPAIR 1 FIG. 201. NO FURTHER DEFECTS NOTED</P>)
CORROSION ON SEAT TRACK/FLOOR BEAM AT LBL 11.33 AT STA. 1740.(<P>CLEANED AREA ON SEAT TRACK/FLOOR BEAM AT LBL 11.33 AT STA. 1740 AT MAIN CARGO DECK. NO CORROSION NOTED PER SOPM 20-30-03 PAR. 1.A. REV 153 & SRM 53-60-52-001-1 FIG. 001 REV 102. NO FURTHER DEFECTS NOTED</P>)
CORROSION FOUND ON FLANGE OF LH BODY LANDING GEAR BEARING CAP.(<P>REMOVED AND REPLACED LH BODY GEAR BEARING CAP PER B747 SRM 53-40-90-2R-1 REPAIR 1 FIG. 201.&NBSP;<SPAN>NO FURTHER DEFECTS NOTED.</SPAN></P>)
CORROSION ON SEAT TRACK AT LBL 11.33 BETWEEN STA. 760-770 MAIN DECK CARGO.(<P>CLEANED AREA ON SEAT TRACK AT LBL 11.33 BETWEEN STA. 760-770 AT MAIN CARGO DECK, NO CORROSION NOTED PAR. 1.A REV 153 SOPM 30-20-80. NO FURTHER DEFECTS NOTED.</P>)
CORROSION AT SEAT TRACK/FLOOR BEAM AT LBL 11.33 AND STA 1635 AFT CARGO COMPARTMENT.<BR>(<P STYLE="MARGIN-BOTTOM: .0001PT; LINE-HEIGHT: NORMAL;"><SPAN>REPAIRED SEAT TRACK/FLOOR BEAM FROM STA 1590 TO STA. 1650 PER B747 SRM 53-00-52-2R-12 REPAIR 12 AFT CARGO COMPARTMENT.</SPAN></P>)
CORROSION ON SEAT TRACK/FLOOR BEAM AT RBL 11.33 AMD STA 1710 AFT CARGO COMPARTMENT.(<P STYLE="MARGIN-BOTTOM: .0001PT; LINE-HEIGHT: NORMAL;">REPLACED 2 SECTIONS OF SEAT TRACKS FROM PREVIOUS REPAIR STA. 1610 TO 1766.5 TO FACTORY SPLICE AND SECOND SECTION FROM 1766.5 TO STA 1910 TO PREVIOUS REPAIR SPLICE RBL 11.33 PER B747 SRM 53-00-52-2R-12 REPAIR 12. <SPAN>NO FURTHER DEFECTS NOTED.
CORROSION FOUND AT INNER FACE ON LH BODY LANDING GEAR LOWER BUSHING (INNER BEARING CAP).<BR>(<P>REMOVED AND REPLACED BUSHING PER B747 SRM 53-40-90-2R-1 REPAIR 1 AND B747 AMM 32-13-01-004-001 AND 32-13-01-404-022.&NBSP;<SPAN>NO FURTHER DEFECTS NOTED.</SPAN></P>)
CORROSION ON SEAT TRACK/FLOOR AT RBL 11.33 AND STA. 1675 AFT CARGO COMPARTMENT.(<P STYLE="MARGIN-BOTTOM: .0001PT; LINE-HEIGHT: NORMAL;">REPLACED TWO EACH SECTIONS OF SEAT TRACKS FROM PREVIOUSLY REPAIR STA 1610 TO 1766.5 TO FACTORY SPLICE AND 2ND SECTION FROM STA. 1766.5 TO STA 1910 TO PREVIOUS REPAIR RBL 11.33 PER B747-400F SRM 53-00-52-2R-12 REP 12 REV 102. REPAIRED ON HM627-20061 AFT CARGO COMPARTMENT. NO FURTHER DEFECTS NOTED.</P>)
CORROSION ON SEAT TRACK AT LBL 11.33 BETWEEN STA. 770 TO 785 AT MAIN CARGO DECK.(<P>CLEANED AREA ON SEAT TRACK AT LBL 11.33 BETWEEN STA. 770-785 AT MAIN DECK CARGO DECK. NO CORROSION NOTED. PER BSOPM 20-30-80 PAR. 1.A. REV 153.&NBSP;NO FURTHER DEFECTS NOTED.</P>)
FL320 EICAS MESSAGE EQUIP COOLING. RETURNED TO MIA. REPEAT WRITE UP. AFTER LANDING, EICAS MESSAGE RETURNED(<P>INSTALLED CLAMP ON WATER SEPERATOR IAW AMM 21-51-05-402-025. REACTIVATED PACK 2. OPS CHECK GOOD. DMI 220071 CLOSED.</P>)
SUSPECTED LIGHTNING STRIKE DEPARTING UIO, RETURNED TO UIO, HEAVY WEIGHT LANDING, BRAKE TEMPERATURE CAUSED TIRE FUSE PLUGS TO MELT ON MAIN LANDING GEAR TIRES #1, 2, 3, 4, 5, 6, 7, 8 AND 10.(<P>UPON LANDING, COMPLETED LIGHTING STRIKE INSP IAW AMM 05-51-13, OVERWEIGHT LANDING INSPECTION IAW AMM 05-51-39. LH BODY AND WING GEAR AND RH BODY GEAR AXLE INSPECTION WAS ACCOMPLISHED BY AAR FAA CRS# VQ4R605M REF WO: 440844, NO DEFECT NOTED. R/R BRAKES #1, 2, 3, 4, 5, 6, 7, 8, 10 IAW AMM 32-41-15 AND MAIN LANDING TIRES #1, 2, 3, 4, 5, 6, 7, 8, 9 AND 10 IAW AMM 32-45-01</P>)
LIGHTNING STRIKE DURING CLIMB, AIR TURN BACK. OVERWEIGHT LANDING AND HIGH ENERGY STOP RESULTED IN 9 MELTED MAIN LANDING GEAR TIRE FUSE PLUGS AND DEFLATION OF TIRES.(<P>AXLES NEED REPLACEMENT. MX CURRENTLY IN WORK PER AMM 05-51-10.</P>)
EXISTING REPAIR ON AFT CGO FRAME WEB STA 1620 LBL 5.5(<P>1) REMOVED EXISTING REPAIR IAW SRM 51-40-02-0G-0 REV 97. 2) PERFORM NDT INSPECTION REFER TO JOB CARD ATTACHING SH 0399166. 3) REPAIRED DAMAGE AREA IAW SRM 51-40-02-0G-0 REV 97, SRM 53-60-07-2R-8 REV 97 & EI T2023A53M-1036 REV 0. 4) ACCOMPLISHED EI T2023A53M-1036 REV 1. 5) JOB COMPLETED</P>)
CRACKON LH UPPER DECK FLOOR BEAM AFTER CHANNEL OF STA 820(<P>1) REMOVE THE DAMAGE AREA IAW SRM 51-40-02-0G-0 & 53-20-30-2R-2 REV 97. 2) REPAIR THE TENSION TIE AFTER CHANNEL IAW SRM 53-20-30-2R-2 REV 97. 3) CONDITION CHECK NORMAL & JOB COMPLETED</P>)
DEVIATION - DURING PFM 4453A087 PART 2, FOUND 2 EXISTING FASTENERS NO CONNECT WITH FRAME AT STA 500 RH SIDE(<P>1) PFM EI T2023A53M-875 SEQUENCE A REV 0. 2) ACCOMPLISHED EI T2023A53M-875 REV 1 AND CONDITION CHECK NORMAL</P>)
CORROSION ON THE FUSELAGE SKIN AT 2-42L BETWEEN STA 1720 & STA 1740(<P>1) REMOVED THE AFFECTED FASTENERS IAW SRM 51-40-02-0G-0 REV 97. 2) PERFORMED EI T2023A53M-834 SEQUENCE A REV 0. 3) ACCOMPLISHED EI T2023A53M-834 REV 1 & CONDITION CHECK NORMAL. 4) RECORD THE REPAIR DOUBLER IS CONFIGURATION 2, REFER TO EI 4453A488 PART 2 STEP 4 REV 11 AND JOB COMPLETED</P>)
DEFORM - FOUND MAIN DECK SEAT TRACK FLOOR COVER DEFORM STA 1730 RBL 75(<P>1) REPAIR DAMAGE AREA IAW SRM 53-00-52-2R-13 REV 97 & BOEING DWG 65B38251 SH 75 REV - & 65B38251 SH 32 REV -. 2) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
FOUND M/D FLOOR STRUCTURE SUBSTITUTE TRACK CRACK AT STA 1485 RBL 75.92(<P>1) REPAIR DAMAGE AREA IAW SRM 53-00-52-2R-13 REV 97 & BOEING DWG 144U0882 SH 3 REV B & 65B38251 SH 32 REV -. 2) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
BROKEN - SKIN AND CAP, RH WING INBD AILERON T/E WEDGE OUTBD END(<P>1) PERFORM REPAIR OF BROKEN SKIN DAMAGE FOUND ON RH WING INBD AILERON T/E OUTBD SIDE. PLEASE REFER TO THE JOB CARD ATTACHING SHEET FOR DETAILED REWORK INFO. 2) CONDITION CHECK IS GOOD.</P>)
DEVIATION - DURING PERFORM 4453A087 PART 2 FOUND EXISTING STRAP HOLES SEM 5 EACH AT STA 480 RH SIDE(<P>1) PERFORM DEVIATION AND PERFORM REPAIR IAW EI T2023A53M-835 REV 1. 2) ACCOMPLISHED EI T2023A53M-835 REV 2. 3) JOB COMPLETED</P>)
FOUND M/D CARGO FLOOR STRUCTURE CORROSION AT STA 2240 LBL 88 TO 85(<P>1) REPAIR DAMAGE AREA IAW EI T2023A53M-900 REV 0 AND SRM 53-00-51-02R-3 REPAIR 3 REV 97. 2) INSTALL REPAIR PARTS IAW EI T2023A53M-900 REV 0 AND SRM 53-00-51-2R-3 REPAIR 3 REV 97 & BOEING DWG 65B38112 SH 13 REV -, 146U0125 SH 89 REV A. 3) ACCOMPLISHED EI T2023A53M-900 REV 1. 4) JOB COMPLETED</P>)
FOUND M/D CGO FLOOR STRUCTURE CORROSION AT STA 2240 RBL 59 TO 80(<P>1) REPAIR DAMAGE AREA IAW EI T2023A53M-902 REV 0 AND SRM 53-00-51-2R-3 REPAIR 3 REV 97. 2) INSTALL REPAIR PARTS IAW EI T2023A53M-902 REV 0 AND SRM 53-00-51-2R-3 REPAIR 3 REV 97 AND BOEING DWG 65B38112 SH 14 REV -, 65B38251 SH 62 REV A. 3) ACCOMPLISHED EI T2023A53M-902 REV 1. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
CRACK ON SHEAR TIE AT STA 1000 RBL 57.50 WL195(<P>1) REMOVED DAMAGE PARTS IAW SRM 51-40-02-0G-0 REV 97. 2) REPAIR DAMAGE AREA IAW EI T2023A53M-1018 SEQUENCE A REV 0. 3) INSTALLED NEW PARTS IAW SRM 51-40-02-0G-0 REV 97 AND EI T2023A53M-1018 SEQUENCE A REV 0. 4) COMPLETED JOB IAW EI T2023A53M-1018 REV 1. 5) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
CRACK ON SHEAR TIE AT STA 1000 RBL 33.99 WL195(<P>1) REMOVED DAMAGE PARTS IAW SRM 51-40-02-0G-0 REV 97. 2) REPAIRED DAMAGE AREA IAW EI T2023A53M-1018 SEQUENCE A REV 0. 3) INSTALLED NEW PARTS IAW SRM 51-40-02-0G-0 REV 97 AND EI T2023A53M-1018 SEQUENCE A REV 0. 4) ACCOMPLISHED JOB IAW EI T2023A53M-1018 REV 1. 5) EI ATTACH TO WO 8158034. 6) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
FND M/D BEAM CORROSION AT STA 2100 RBL 100(<P>1) REPAIR DAMAGE AREA IAW SRM 53-00-51-2R-3 REV 97 AND EI T2023A53M-1103 SEQUENCE A REV 0 AND BOEING DWG 65B38105 SH12 REV -, 65B38251 SH 62 REV A, 65B38251 SH 33 REV -, 65B38251 SH 67 REV A, 65B38406 SH 48 REV A. 2) ACCOMPLISHED EI T2023A53M-1103 REV 1. 3) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
RH OUTBD MID FLAP WBL 822 FWD RIB AND CONTROL ASSY(<P>1) REMOVED DAMAGE PARTS IAW SRM 51-40-02-0G-0 REV 97. 2) FABRICATED PARTS IAW EI T2023P57M-823 REV 0 & EI T2023A57M-802 REV 1. 3) INSTALLED FABRICATED PARTS IAW SRM 51-40-02-0G-0 REV 97 DRAWING 65B08527 SH 6 REV C, 65B01962 SH 2 REV B & 113U0007 SH 2 REV 3. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
DEFORM - FOUND M/D SEAT TRACK FLOOR COVER DEFORM AT STA 1630 LBL 75(<P>1) REPAIR DAMAGE AREA IAW SRM 53-00-52-2R-13 REV 97 AND BOEING DWG 65B38251 SH 62 REV A, 65B38251 SH 75 REV -, 65B38251 SH 32 REV -. 2) JOB COMPLETED</P>)
FOUND M/D CGO SEAT TRACK CORROSION BETWEEN STA 1770 TO STA 1900 LBL 11.33(<P>1) REMOVED AFFECTED FASTENERS IAW SRM 51-40-02-0G-0 REV 97. 2) PERFORMED EI T2023A53M-1035 REV 0 SEQUENCE A. 3) INSTALLED FASTENERS IAW SRM 51-40-02-0G-0 REV 97 AND DWG 65B38253 SH 49 REV -, 65B38253 SH 50 REV A, 65B38253 SH51 REV A, & 65B38253 SH 1 REV AP. 4) ACCOMPLISHED EI T2023A53M-1035 REV 1. 5) JOB COMPLETED</P>)
EXISTING REPAIR ON AFT CGO FRAME WEB NEAR STA 1880 LBL 45.5(<P>1) REMOVED EXISTING REPAIR IAW SRM 51-40-02-0G-0 REV 97. 2) PERFORMED NDT INSPECTION REFER TO JOB CARD ATTACHING SH 0399168. 3) REPAIRED DAMAGE AREA IAW SRM 51-40-02-0G-0 REV 97, SRM 53-60-07-2R-8 REV 97 AND EI T2023A53M-1032 REV 0. 4) ACCOMPLISHED EI T2023A53M-1032 REV 1. 5) JOB COMPLETED</P>)
CORROSION DAMAGE ON UPPER CHORD OF MAIN DECK FLOOR BEAM AT STA 1760, BETWEEN RBL 45.50 AND RBL 55(<P>1) REPAIR DAMAGE AREA IAW EI T2023A53M-919 REV 0 AND SRM 53-00-51-2R-3 REPAIR 3 REV 97 AND BOEING DWG 65B38088 SH 27 REV -, 65B38088 SH 28 REV -, 457U4040 SH 12 REV -, 457U4040 SH 14 REV A, 457U4040 SH 4 REV B. 2) ACCOMPLISHED EI T2023A53M-919 REV 1. 3) CONDITIONED CHECK NORMAL AND JOB COMPLETED</P>)
FOUND MAIN DECK CARGO FLOOR BEAM STRUCTURE CORROSION AT STA 1640 LBL 33.99 AND LBL 75.92(<P>1) REPAIR DAMAGE AREA IAW EI T2023A53M-918 REV 1 AND SRM 53-00-51-2R-3 REV 97 AND BOEING DWG 65B38082 SH 14 REV -, 65B3082 SH 13 REV A. 2) ACCOMPLISHED EI T2023A53M-918 REV 2. 3) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
EXISTING REPAIR ON AFT CGO FRAME UPPER CHORD STA 1640 RBL 15(<P>1) REMOVED EXISTING REPAIR IAW SRM 51-40-02-0G-0 REV 97. 2) ACCOMPLISHED EI T2023A53M-1056 SEQUENCE A REV 1. 3) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
CORROSION ON THE FUSELAGE SKIN AT S-43L BETWEEN STA 1700 - STA 1720(<P>1) REMOVED EXISTING REPAIR PARTS IAW SRM 51-40-02-0G-0 REV 97. 2) PERFORM EI T2023A53M-870 SEQUENCE A REV 0. 3) ACCOMPLISHED EI T2023A53M-870 REV 1 AND CONDITION CHECK NORMAL. 4) RECORD THE REPAIR DOUBLER IS CONFIGURATION 2 REFER TO EO 4453B088 PART 2 STEP 4 REV 11 AND JOB COMPLETED</P>)
EXISTING REPAIR ON LH V.S.T. CHORD BETWEEN FRONT SPAR AND REAR SPAR AT FIN STA 595.00 FIN WL378.15 LBL 7(<P>1) REMOVED THE EXISTING REPAIR PARTS IAW SRM 51-40-02-0G-0 REV 97. 2) PERFORMED EI T2023A55M-1062 REV 1 SEQUENCE B. 3) ACCOMPLISHED EI T2023A55M-1062 REV 2. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
EXISTING REPAIR DOUBLER ON NOSE CGO DOOR SKIN STA 160 BETWEEN S024AR AND S-26R(<P>1) REMOVED EXISTING REPAIR DOUBLER IAW SRM 51-40-02-0G-0 REV 97. 2) PERFORM THE REPAIR IAW EI T2023A52M-1055 REV 1. 3) ACCOMPLISHED EI T2023A52M-1055 REV 2. 4) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
CRACK - LONGERON, FUSELAGE EXTERNAL SURFACE NEAR S-331 STA 1480(<P>1) REMOVE THE DAMAGE LONGERON FITTING IAW SRM 51-40-02-0G-0 REV 97 AND EO 4453A818 PART 3 STEP 4 & 6 REV 19. 2) ACCOMPLISHED THE REPAIR AREA IAW EI T2023A53M-935 REV 2, SRM 51-40-02-0G-0 REV 97, EO 4453A818 PART 3 STEP 9-10, DWG 65B15254 SH 10 REV G, SH 16 REV F, 65B01162 SH 14 REV A & 65B15085 SH 3 REV J. 3) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
CRACK ON THE WEB OF LH STA 1480 BULKHEAD FRAME WEB(<P>1) REMOVE THE AFFECTED FASTENERS IAW SRM 51-40-02-0G-0 REV 97. 2) REPAIR THE DAMAGE AREA IAW EI T2023A53M-1037 REV 1, SRM 51-40-02-0G-0 REV 97 & SRM 53-40-08-2R-1 REPAIR 1 REV 97. 3) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
EXISTING REPAIR ON NOSE CGO DOOR STRINGER STA 180 - STA 200 S-4R(<P>1) REMOVED EXISTING REPAIR IAW SRM 51-40-02-0G-0 REV 97. 2) REPAIR STRINGER IAW EI T2023A52M-1042 REV 0. 3) ACCOMPLISHED EI T2023A52M-1042 REV 1. 4) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
FOUND M/D CGO SIDEWALL FRAME CRACK AT STA 1860 S12R - S13R(<P>1) REMOVED DAMAGED AREA ACCESS IAW SRM 51-40-02-0G-0 & SRM 53-60-07-2R-5 REV 97. 2) PERFORM NDT INSP DAMAGE AREA FREE OF CRACK REFER TO JOB CARD ATTACHING SHEET 0389509. 3) PERFORM EI T2023A53M-985 SEQUENCE A REV 0. 4) ACCOMPLISHED EI T2023A53M-985 SEQUENCE B REV 1 AND DWG 146U1860 SH 47 REV A, 146U3732 SH 20 REV 0 & 146U1312 SH89 REV B. 5) ACCOMPLISHED EI T2023A53M-985 REV 2. 6) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
FOUND M/D CGO FLOOR STRUCTURE CORROSION AT STA 480 BETWEEN 55.20 AND LBL 80.00(<P>1) REMOVE SUPPORT ANGLE IAW SRM 51-40-02-0G-0 REV 97. 2) FABRICATE SUPPORT ANGLE IAW EI T2023A53M-1033 REV 20, T2023A53M-1034 REV 0, T2023P53M-1023 & T2023P53M-1024 REV 0. 3) REPAIR DAMAGE AREA IAW EI T2023A53M-921 REV 1, SRM 53-00-51-2R-3 REV 97, BOEING DWG 284U1103 SH 14 REV -, 284U1103 SH 15 REV -, 284U1120 SH 6 REV -, 141U5348 SH 1 REV E. 4) PERFORM EI T2023A53M-921 REV 2 SEQUENCE C. 5) ACCOMPLISHED EI T2023A53M-921 REV 3, T2023A53M-1433 & T2023A53M-1034 REV 1 6) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
FOUND M/D CGO FLOOR STRUCTURE CORROSION AT STA 800 BETWEEN RBL 75.92 AND 98.58(<P>1) REPAIR DAMAGE AREA IAW EI T2023A53M-913 REV 0 T2023P53M-1025 REV 0, SRM 53-00-51-2R-3 REV 97, BOEING DWG 65B38040 SH8 REV A, 65B38040 SH9 REV D & 65B38250 SH17 REV A. 2) ACCOMPLISHED EI T2023A53M-913 REV 1 & T2023P53M-1025 REV 0. 3) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
CORROSION ON SKIN INNER SURFACE TOTAL 21 EACH, WHEN PERFORM SB 747-53A2878(<P>1) PERFORM EI T2023A53M-854 SEQUENCE A REV 0. 2) PERFORM EI T2023A53M-854 SEQUENCE B REV 1. 3) PERFORM EI T2023A53M-854 SEQUENCE C REV 2. 4) PERFORM EI T2023A53M-854 SEQUENCE D REV 4. 5) ACCOMPLISH EI T2023A53M-854 REV 4. 6) ACCOMPLISH EI T2023A53M-854 REV 5. 7) JOB COMPLETED AND CONDITION CHECK NORMAL</P>)
CORROSION - BRACKET FWD WING TO BODY FAIRING SUPPORT BRACKET STA 955 TO STA 982 LBL 4(<P>1) REMOVED DAMAGE PART IAW SRM 51-40-02-0G-0 REV 97. 2) INSTALLED NEW PART IAW SRM 51-40-02-0G-0 REV 97 & DWG 65B06976 SH 2 REV G. 3) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
CORROSION DAMAGE ON ANGLE OF M/D CGO FLOOR STRUCTURE AT STA 2280 RBL 62(<P>1) REMOVE DAMAGE PARTS IAW SRM 51-40-02-0G-0 REV 97. 2) FABRICATE PARTS IAW EI T2023P53M-887 REV 0. 3) INSTALL FABRICATED PARTS IAW SRM 51-40-02-0G-0 REV 97, DWG 457U1061 SH 4 REV C & DWG 146U342 SH 3 REV B. 4) JOB COMPLETED</P>)
CORROSION - BRACKET FWD WING TO BODY FAIRING FRAME SUPPORT BRACKET GWD AND AFT SIDE STA 920 S47 - S47R(<P>1) REMOVE DAMAGE PARTS IAW SRM 51-40-02-0G-0 REV 97. 2) INSTALLED NEW PARTS IAW SRM 51-40-02-0G-0 REV 97, DWG 65B06704 SH 2 REV 3 & 142U0130 SH 1 REV A. 3) JOB COMPLETED</P>)
FOUND #6 FLAP TRACK INBD SIDE CONTACT WITH SIDE LOAD FITTING SURFACE CORROSION(<P>1) REF EI T2023A57M-923 REV 1 SEQUENCE A, PERFORM #6 FLAP TRACK PERMANENT REPAIR. 2) CONDITION CHECK NORMAL</P>)
FOUND M/D CGO FLOOR FITTING CORROSION AT STA 290 RBL 61 STA 300 RBL 61 & STA 320 RBL 56 TTL: 3 EACH(<P>1) IAW AMM WUBTASK 53-44-00-212-011 REV 107 & AMM SUBTASK 53-44-00-02-001 REV 107 REPLACED M/D CGO FLOOR FITTING AT STA 290 RBL 61 & STA 300 RBL 61 TTL: 2 EACH. 2) IAW AMM SUBTASK 53-44-00-212-011 REV 107 REMOVED M/D CGO FLOOR FITTING AT STA 320 RBL 56 TTL: 1 EACH. 3) ACCOMPLISHED FABRICATED PART IAW EI T2023A25M-932 REV 1. 4) IAW AMM WUBTASK 53-44-00-020-001 REV 107 INSTALLED M/D CGO FLOOR FITTING AT STA 320 RBL 56 TTL: 1 EACH. 5) JOB COMPLETED AND CONDITION CHECK NORMAL. FITTING SN: 69B2027-2, 69B62078-2 & 69B62030-2</P>)
FOUND FUNCTION FAIL AT RH WLG ALTERNATE EXTENSION ROTARY ACTUATOR(<P>1) IAW AMM 32-36-01-004-001 REV 107 & AMM 32-36-01-404-009 REV 107 STEP 3.A TO F(4) R/R RH ALTERNATE ELEC ACTUATOR. 2) IAW AMM 32-36-01-404-009 REV 107 STEP F(5) PERFORM RH WLG ALTERNATE EXTENSION TEST. 3) CONDITION CHECK NORMAL</P>)
WHEN PERFORM EMERGENCY LIGHT BATTERY PACKS CAPACITY TEST FOUND M5168, M5169 & M5170 BATTERY FAIL(<P>1) IAW AMM 33-51-04-902-001-001 REV 107 R/R EMERGENCY LIGHT BATTERY ASSY AT M5168, M5169 & M5170. 2) IAW AMM 33-51-04-902-001-001 REV 107 PERFORMED EMERGENCY LIGHT BATTERY ASSY INSTALLATION TEST AND THE RESULT WAS GOOD. SN: 91862, 91861 & 91863</P>)
FOUND M/D FLOOR STRUCTURE SUBSTITUTE TRACK CRACK AT STA 990 LBL 75.92(<P>1) REPAIR DAMAGE IAW SRM 53-00-52-2R-13 REV 97 AND DWG 65B16004 SH 4 REV A. 2) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
FOUND M/D FLOOR STRUCTURE SUBSTITUTE TRACK CRACK AT STA 990 RBL 75.92(<P>1) REPAIR DAMAGE AREA IAW SRM 53-00-52-2R-13 REV 97 REV 97 AND DWG 65B16004 SH 4 REV A. 2) CONDITION CHECK NORMAL AND JOB COMPLETED</P>)
REINSPECTION OF DENT AT FWD CARGO FUSELAGE STATION 560 ( 15 INCHES FROM BOTTOM OF DOOR CUT OUT ) (PART II OF EO 4453C212, DUE EVERY 5 FLIGHT CYCLES )(<P>ACCOMPLISHED ATLAS AIR&NBSP; EO # 4453C212 PART # 3&NBSP; PERMANENT REPAIR AT&NBSP; FWD FUSELAGE BY STA 560 BOTTOM OF DOOR&NBSP; CUT OUT SRM 53-00-01-1A-1.</P> / <P>PERMANENT NDT HFEC INSPECTION&NBSP; FLOURESENT THE CUT OUT&NBSP; AND OPEN&NBSP; HOLE&NBSP; AT FASTENER&NBSP; LOCATION,&NBSP; NO CRACK IND&NBSP; NOTED ACT NDTM&NBSP; 51-00-00.</P>)
# 3 ENGINE FUEL VALVE STATUS MSG ACTIVE(<P>R/R HMU FUEL SOV SW. IAW AMM 73-21-23. OPS CK GOOD. DMI 170784 CLOSED.</P>)
F/O'S AFT INBOARD SEAT TRACK FOUND CRACKED AT FORWARD END.(<P>F/O'S SEAT REMOVED AND INSTALLED IAW AMM 25-11-01-404-031. SEAT TRACK REPLACED IAW AMM 25-11-01-824-127. SEAT OPERATIONAL TEST OK IAW AMM 25-11-00/201.</P>)
CF6-80C2B1F, FAN FWD SHAFT WITH 6 EA FPI INDICATIONS ON AREA FB NEAR THE VENT HOLES. 1 EA INDICATION CONFIRMED AS A CRACK. PER THE GEK92451 TASK 72-21-05-230-001-051 A.(2) INDICATIONS IN AREA FA AND FB ARE NOT PERMITTED. PART IS UNSALVAGEABLE.
SMOKE CREW REST EICAS MSG ON APPROACH(<P>TRANSFERRED TO MDDR 144634 IAW MEL 26-14-02-01-02, CAT C.</P>)
SMOKE CREW REST EICAS ADVISORY MESSAGE STARTED AT 0220Z. NO EVIDENCE OF SMOKE.RESET SMOKE DETECTOR AND OPS / CHECKED IAW AMM 26-14-50. OPS CHECK GOOD. NO DEFECTS NOTED.
SMOKE CREW REST EICAS MESSAGE DURING DECENT(<P ><SPAN>PERFORMED CREW REST SMOKE / TEST IAW AMM 26-14-50/501. OPS CHK GOOD.</SPAN></P>)
M/D STA 790 LBL 11 SEAT TRACK FOUND CRACK.(<P>M/D STA 750 - 790 LBL 11 SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12</P>)
M/D L5 DOOR STA 2231 S-16L FRAME FASTENER HOLE FOUND CRACK.(<P>M/D L5 DOOR STA 2231 S-16L FRAME FASTENER HOLE REPAIR AS PER SRM 53-60-15-2R-5</P>)
RHW #18 L/E V/C FLAP BULLNOSE FAIRING SKIN I/B EDGE CHAFING.(<P>RHW #18 L/E V/C FLAP BULLNOSE SKIN I/B EDGE CHAFING AREA. REPAIRED AS PER RI-57-00-14394 REV A.</P>)
BS 938-1000 S38L DRAG SPLICE LOWER FITTING AREA, SKIN REPAIR CRACK REPAIR.(<P>EO 4453A705 ' CAT B ' PERMANENT REPAIR ACCOMPLISHED ON SKIN ASSEMBLY 65B04116 PER 747-400F SRM 53-20-01 REPAIR 2 AT BS 950 - BS 990, S38L.</P>)
BS 1700 S-41L, SKIN DENT, INSPECTION AND CAT B&NBSP; PERMANENT REPAIR.(<P>EO 4453A541 CAT B PERMANENT REPAIR ACCOMPLISHED AT HKG DURING FEB 2016 C1A1 CHECK BY HAECO.</P>)
LONGERON EXTENSION FITTING INSPECTION, REPAIR AND MODIFICATION - BODY STATION 1480 TO BODY STATION 1540 - SB 747-53A2860 R3 / AD 2020-15-14.(<P>REF EO 4453A818, PERMANENT REPAIR IS PERFORMED.</P>)
SKIN - NOSE WHEEL WELL AFT CORNER SKIN PANEL BS 399 AT S-44R. DEVIATION SB 747-53A2305R2 MODIFICATION.(<P>EO 4453B313 CAT B PERMANENT REPAIR IS PERFORMED.</P>)
LH O/B MID FLAP AFT EDGE UPPER SURFACE FOUND DELAM.(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5A</P>)
LHW O/B MID FLAP UPPER SURFACE SCREW HOLE FOUND ELONGATED.(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5K.</P>)
M/D STA 1920 - 2020 L/H DADO PANEL FOUND CRACK.(<P>M/D STA 1920 - 2020 L/H DADO PANEL REPAIRED AS PER RI-25-00-14385 REV A.</P>)
M/D STA 1585 RBL 11 SEAT TRACK FOUND CRACK.(<P>M/D STA 1570-1610 RBL 11 SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12</P>)
M/D STA 1070 LBL 11 SEAT TRACK FOUND CRACK.(<P>M/D STA 1000 - 1080 LBL 11 SEAT TRACK REPAIRED AS PER SRM 53- 40-52-2R-3 REPAIR 3.</P>)
LHW I/B FORE FLAP L/E FAIRING FOUND DELAM.(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5A.
RH O/B FLAP FORE FLAP O/B TOP PANEL FOUND PUNCH HOLE.(<P>PERFORMED PERMANENT METAL TO METAL HOT BOND REPAIR AS PER SRM 51-70-10 REPAIR 2 FIG 203.</P>)
RHW O/B MID FLAP L/E FAIRING FOUND DELAMINATE FORM I/B 116".(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AT RHW O/B MID FLAP L/E FAIRING AS PER SRM 51-70-07 PAR 5A.</P>)
RHW O/B MID FLAP L/E FAIRING FOUND DELAMINATION FROM I/B 192".(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5A.</P>)
RH O/B MID FLAP UPPER SURFACE SCREW HOLE ELONGATED.(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-09 PAR 5K.</P>)
LONG EXTENSION FITTING INSPECTION, REPAIR AND MODIFICATION - BODY STATION 1480 TO STATION 1540 - SB 747-53A2860 R3 / AD 2020-15-14.(<P>REF EO 4453A818, PERMANENT REPAIR IS PERFORMED.</P>)
LH O/B FORE FLAP L/E FAIRING FOUND DELAM.(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5A.</P>)
LHW O/B MID FLAP UPPER SURFACE SCREW HOLE FOUND ELONGATED.(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5K.</P>)
SKIN - NOSE WHEEL WELL AFT CORNER SKIN PANEL BS 399 AT S44L. DEVIATION SB 747-53A2305R2 MODIFICATION.(<P>EO 4453B313 CAT B PERMANENT REPAIR IS PERFORMED.</P>)
M/D STA 1620 - 1720 LH DADO PANEL FOUND CRACK.(<P>M/D STA 1620 - 1720 LH DADO PANEL REPAIRED AS PER RI-25-00-14384 REV A.</P>)
LHW O/B MID FLAP UPPER SURFACE SCREW HOLE FOUND ELONGATED.(<P>PERFORMED PERMANENT COMPOSITE HOT BOND REPAIR AS PER SRM 51-70-07 PAR 5K.</P>)
LHW I/B AFT FLAP UPPER SKIN FOUND CORROSION.(<P>LHW I/B AFT FLAP UPPER SKIN CORROSION AREA REPAIRED AS PER SRM 57-53-01-1A-0.</P>)
RHW I/B MID FLAP UPPER SKIN AFT T/E FOUND CORROSION.(<P>RHW I/B MID FLAP UPPER SKIN AFT T/E CORROSION AREA REPAIRED AS PER SRM 57-53-01-1A-0.</P>)
LHW I/B MID FLAP UPPER SKIN FOUND CORROSION.(<P>LHW I/B MID FLAP UPPER SKIN CORROSION AREA REPAIRED AS PER SRM 57-53-01-1A-0.</P>)
M/D STA 665 LBL 11 SEAT TRACK FOUND CRACK.(<P>M/D STA 650 - 750 LBL 11 SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12</P>)
M/D STA 1917 RBL 11 SEAT TRACK FOUND CRACK.(<P>M/D STA 1910-1950 RBL 11 SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12</P>)
M/D STA 1515 RBL 11 SEAT TRACK FOUND CRACK.(<P>M/D STA 1480 - 1570 RBL11 SEAT TRACK REPAIRED AS PER SRM 53-00-52-2R-12.</P>)
MAIN DECK CARGO LOOP 12B, 11B MULTIPLE MD CARGO LOOP A STATUS MESSAGE PRODUCED WITH CGO DET 12 MAIN DECK MAIN DECK FIRE IND CAME AND EXTINGUISHED, NO FIRE PRESENT. CLEANED, INSPECTED AND TESTED ALL AFFECTED SMOKE DETECTORS, IAW AMM 26-14-00. OPERATIONS CHECK GOOD.
REJECTED TAKEOFF BELOW 80 KNOTS. RTO DUE TO STAB TRIM CONFIG. RAN TRIM +/-, RESET TRIM, TRIM WITHIN GREEN BAND.&NBSP; (NOTE: FLIGHT CREW ABORTED IN ONT AND DID NOT INFORM MX, DEPARTED TO MEM.)(<P>UPON ARRIVAL TO MEM, PERFORMED HIGH ENERGY STOP INSPECTION IAW B747-400 AMM TASK 05-51-10-202-001, NO DEFECTS NOTED. PERFORMED STAB TRIM CONTROL SYSTEM CHECK IAW B747-400 AMM TASK 27-41-00-715-007, NO DEFECTS NOTED.&NBSP;&NBSP;<BR /></P>)
OVERHEAD HATCH WILL NOT CLOSE OR OPEN.(<P>ADJUSTED DOOR MECHANISM AS PER AMM 52-21-01, OPS CHECK NORMAL.</P>)
STAB TRIM DISPLAYED OUT OF GREEN BAND. NOSE DOWN BAND DID NOT ILLUMINATE WHEN INDICATOR LIGHTS TESTED. PERFORMED GREEN BAND DISAGREE TEST PER FIM 27-41-944. STAB GREEN BAND OPS TEST NORMAL IAW MM 27-48-60-865-602. NOSE PRESSURE SWITCH CLEANED.
ANTI-SKID EICAS MSG BEFORE 80KTS. RTO AT 75KTS. RETURN TO BLOCKS. FOUND #10 BRAKE ANTISKID TRANSDUCER FAULTY, PLACED ON DEFERRAL. <BR /></P>)
CABIN-STA 1650 LBL 11.33" SEAT TRACK FOUND CORRODED.(<P><SPAN>CABIN-STA 15650.45- TO STA 1730.45 LBL 11.33" SEAT TRACK REPAIRED IAE.&NBSP;SRM 53-00-52-2R-12 REPAIR 12</SPAN></P>)
CABIN-STA 1710-1713 LBL 11.33" SEAT TRACK FOUND CORRODED.(<P><SPAN>CABIN-STA 1730.45- TO STA 1766.45 LBL 11.33" SEAT TRACK REPAIRED IAE&NBSP;SRM 53-00-52-2R-12 REPAIR 12</SPAN></P>)
M/DECK STA 1050 RBL 11 SEAT TRACK FOUND ELONGATED(<P><SPAN>MID STA1000 TO STA1070.45 RBL 11.33" DAMAGED SEAT TRACK REPAIRED IAW&NBSP;SRM 53-40-52-2R-3 REPAIR3</SPAN></P>)
CABIN-STA 1244 STR 4L LOWER INNER SKIN FOUND SURFACE CORROSION(<P><SPAN>CABIN-STA 1244 STR 4L LOWER INNER SKIN SURFACE CORROSION. REMOVED IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND&NBSP;CHECKED WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
CABIN-STA 1244 STR 5L-6L INNER SKIN FOUND SURFACE CORROSION(<P><SPAN>CABIN-STA 1244 STR 5L-6L INNER SKIN SURFACE CORROSION. REMOVED&NBSP;IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND CHECKED&NBSP;WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
CABIN-STA 1244 STR 6L -7L INNER SKIN FOUND SURFACE CORROSION(<P><SPAN>CABIN-STA 1244 STR 6L-7L INNER SKIN SURFACE CORROSION. REMOVED IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND CHECKED&NBSP;WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
CABIN-STA 1244 STR 7L -8L INNER SKIN FOUND SURFACE CORROSION(<P><SPAN>CABIN-STA 1244 STR 7L-8L INNER SKIN SURFACE CORROSION. REMOVED&NBSP;IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND CHECKED&NBSP;WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
CABIN-STA 1244 STR 8L -9L INNER SKIN FOUND SURFACE CORROSION.(<P><SPAN>CABIN-STA 1244 STR 8L-9L INNER SKIN SURFACE CORROSION REMOVED.&NBSP;IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND CHECKED&NBSP;WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
M/D STA 2140-2197 LBL 11.33" SEAT TRACK CROWN FOUND CORROSION.(<P><SPAN>CABIN-STA 2130.45-STA 2210.45 LBL 11.33" DAMAGED SEAT TRACK.&NBSP;REPAIRED IAW SRM 53-00-52-2R-12 REPAIR 12</SPAN><BR /></P>)
CABIN-STA 1353 STR 16R LOWER INNER SKIN FOUND SURFACE CORROSION(<P><SPAN>CABIN-STA 1353 STR 16R LOWER INNER SKIN SURFACE CORROSION.&NBSP;REMOVED IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND&NBSP;CHECKED WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
LH SIDE HORIZONTAL STAB UPPER SKIN AND UPPER REAR SPAR CHORD ZONE B AREA FASTENER HOLE FOUND CRACKED.(<P><SPAN>EMP -STA 2598 HORI STAB LH UPPER SKIN# 14 FASTENER HOLE CRACK&NBSP;AREA FREEZE PLUG REPAIRED IAW RL-55-10-1377 REV.A</SPAN></P>)
LH DOOR L1853 EMERGENCY LT FOUND INOP(<P>LH DOOR L1853 EMERGENCY&NBSP;LT REPLACED AND TEST NORMAL IAW AMM 33-51-05.</P>)
CABIN-STA 1353 STR 17R-18R INNER SKIN FOUND SURFACE CORROSION(<P><SPAN>CABIN-STA 1353 STR 17R-18R INNER SKIN SURFACE CORROSION.&NBSP;REMOVED IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND&NBSP;CHECKED WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
LH DOOR L1854 EMERGENCY LT FOUND INOP(<P>LH DOOR L1854 EMERGENCY LT ASSY REPLACED AND OPERATIONAL TEST PASSED IAW AMM 33-51-05.</P>)
CABIN-STA 1244 STR 9L -10L INNER SKIN FOUND SURFACE CORROSION(<P><SPAN>CABIN-STA 1244 STR 9L-10L INNER SKIN SURFACE CORROSION REMOVED.&NBSP;AW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND CHECKED&NBSP;WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED.&NBSP;</SPAN></P>)
CABIN-STA 1477 STR 9L LWR INNER SKIN FOUND SURFACE CORROSION.(<P><SPAN>CABIN-STA 1477 STR 9L LOWER INNER SKIN SURFACE CORROSION.&NBSP;REMOVED IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND&NBSP;CHECKED WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
CABIN-STA 1483 STR 17R LWR INNER SKIN FOUND SURFACE CORROSION.(<P><SPAN>CABIN-STA 1483 STR 17R LOWER INNER SKIN SURFACE CORROSION.&NBSP;REMOVED IAW SRM 51-10-02 AND REPROTECTED IAW SRM 51-20-01 AND&NBSP;CHECKED WITHIN SRM 53-00-01 ALLOWABLE 1 LIMITED</SPAN></P>)
R/H WING LIE SLAT# 17 0/B LWR EDGE FOUND DAMAGED.(<P><SPAN>R/H WING # 17 VC FLAP LIE 0/B SKIN EDGE CRACK AREA REPAIRED IAW&NBSP;RL-57-40-13375 REV.A</SPAN></P>)
R/H WING L/E SLAT# 18 1/B LWR EDGE FOUND DAMAGED(<P><SPAN>RIH WING # 18 VC FLAP LIE 0/B SKIN EDGE CRACK AREA REPAIRED IAW&NBSP;RL-57-40-13375 REV.A</SPAN></P>)
R/H WING UE FLAP PNL STRINGER BONDING ATTACHMENT POSITION FOUND CORROSION.(<P><SPAN>R/H WING LIE FLAP PNL STRINGER BONDING ATTACHMENT POSITION&NBSP;CORROSION REMOVED AND REPAIRED IAW RL-57-40-13376 REV.A</SPAN></P>)
STATUS MESSAGE NR 3 ENGINE CONTROL AT TOUCHDOWN, THE NR 3 ENGINE ROLLED BACK AND SHUT ITSELF DOWN, AS A PRECAUTION, THE NR 3 FUEL CONTROL SWITCH TO CUTOFF. R & R THE CIT SENSOR IAW AMM 73-21-02. OPS CHECKED NORMAL. OK FOR CONTINUED FLIGHT.
BLEED 4 EICAS. FOLLOWED QRH PROCEDURES AND EXPERIENCED ENGINE STALLS AFTER OPENING ENG BLEED 4. ALL GROUND CHECKS ACCOMPLISHED, NO FINDINGS IAW AMM 36-00-00.
THE CAPTAIN REPORTED AN ELECTRICAL ODOR IN THE FLIGHT DECK AREA. THE FORWARD ELECTRONIC-ELECTRICAL EQUIPMENT COMPARTMENT COOLING SUPPLY FAN FAILED.
EQUIPMENT SMOKE STATUS MESSAGE WITH A FAINT ODOR OF SMOKE ON ARRIVAL. A CHECK FOUND TO BE NORMAL, NO SMOKE ODOR, SMOKE DETECTOR INSPECTED, ALSO NORMAL. FIRE TEST AND EQUIPMENT COOLING TEST FOUND NORMAL IAW AMM 26-10-51.
FUNCTIONAL FAIL OF THE ALTERNATE ELECTRICAL LEADING EDGE SYSTEM. REPLACED WIRE W4747-307-188.18Y.18B AND PERFORMED WIRE CONTINUITY CHECK AND RESULT WAS SATISFACTORY IAW WDM 27-81-32, REV 44. REPLACED THE LT L3 PDU, AND PERFORMED INSTALLATION TEST, THE RESULT WAS SATISFACTORY IAW SWPM 20-10-12 REV 64, AMM 27-81-03-002-001 REV 88, AND AMM 27-81-03-402-019 REV 88.
SEAT TRACK DEFORM AT STA 1490 LBL 75.92. REPAIR DAMAGE AREA IAW SRM 53-00-52-2R-13 REPAIR 13 REV 79 AND DWG NO 65B38251 SH75 REV - DWG NR 65B38251 SH62 REV A & 2. JOB COMPLETED AND CONDITION CHECK NORMAL.
FOUND FLOORBEAM UPPER CHORD CORROSION AT STA 1120 RBL 107~109. REMOVE DAMAGED PART IAW SRM 51-40-02 REV 79 & 2. INSTALL NEW PART IAW SRM 51-40-02 REV 79 AND DWG 65B16046 SH3 REV B & 3. JOB COMPLETED AND CONDITION CHECK NORMAL.
FOUND SEAT TRACK CORROSION AT STA 1956 TO STA 2115 LBL 11.33. REPAIR DAMAGED AREA IAW EI NR T2017A53M-539 REV 1 AND DWG NUMBER 65B38253 SHEET 51 REV A & 2. INSTALL THE FLOOR PANELS PLEASE REFER JOB CARD NUMBER 538520102 AND 538580102 & 3. JOB COMPLETED AND CONDITION CHECK NORMAL.
SEAT TRACK BRK AT STA 994.5 RBL 75.92. REPAIR AREA IAW SRM 53-00-52 REPAIR 13 REV 79 AND DWG NR 65B38250 SH17 REV A NR 65B38250 SH9 REV B, NR 65B38250 SH20 REV- AND 65B16004 SH4 REV A & 2. JOB COMPLETED AND CONDITION CHECK NORMAL.
FND FLOORBEAM CORROSION ON THE STA 1500 MAIN DECK FLOORBEAM UPPER CHORD NEAR RBL 23. REPAIR DAMAGE AREA IAW EI NR T2017A53M-529 REV 1 & 2. JOB COMPLETED AND CONDITION CHECK NORMAL.
FND CORROSION ON THE UPPER CHORD OF MAIN DECK FLOORBEAM AT STA 1920 NEAR LBL 95. REPAIR THE DAMAGE AREA IAW EI NR T2017A53M-690 REV 1 & 2. CONDITION CHECK NORMAL AND JOB COMPLETED.
FOUND CORROSION AT UPPER CAP OF MAIN DECK FLOORBEAM AT STA 2140 RBL 94. REPAIR DAMAGED AREA IAW EI NR T2017A53M-518 REV 1 & 2. INSTALL THE FLOOR PANELS PLEASE REFER JOB CARD NUMBER 538580102 & 3. JOB COMPLETED AND CONDITION CHECK NORMAL.
FOUND CORROSION AT UPPER CHORD OF MAIN DECK FLOORBEAM AT STA 980 NEAR LBL 75.92. REPAIR DAMAGED AREA IAW EI NR T2017A53M-527 REV 1 & 2. INSTALL THE FLOOR PANELS PLEASE REFER JOB CARD NUMBER 538260102 AND 538280102 & 2. JOB COMPLETED AND CONDITION CHECK NORMAL.
SKIN CRACK FOUND LT AFT CORNER SKIN PANEL CRACK OF THE NOSE WHEEL WELL AT STA 399 S-44L AND DEVIATIONS WERE FOUND DURING PERFORMING SB 747-53A2305. ACCOMPLISHED EI NR T2017A53M-505 REV 2. REPAIR DAMAGED SKIN REFER TO EO 4453A516 REV 7 & 3. JOB COMPLETED AND CONDITION CHECK NORMAL.
FOUND FLOORBEAM CORROSION AT STA 2300 LBL 52. ACCOMPLISHED EI NR T2017A53M-516 REV 0 & 2. JOB COMPLETED AND CONDITION CHECK NORMAL.
STATUS MESSAGE 28649, FOR RIGHT CENTER WING JETTISON TRANSFER VALVE FAILED. REMOVED RIGHT CENTER WING TANK JETTISON TRANSFER VALVE ACTUATOR IAW AMM 28-31-04-004-001, REV 88. INSTALLED A NEW JETTISON TRANSFER VALVE ACTUATOR AT RIGHT CENTER WING TANK IAW AMM 28-31-04-404-010 REV.88 STEP 3A TO STEP E(2). PERFORM GROUND TEST FOR RT CENTER WING FUEL JETTISON TRANSFER VALVE RESULT WAS SATISFACTORY AND CONDITION CHECK NORMAL IAW AMM 28-31-04-404-010 REV 88, STEP 3E(3), AND AMM 28-31-00-715-066, REV 88.
STRINGER 12R AFT END SEVERED AT BS 2658. REMOVED AND REPLACED THE STRINGER IAW SRM 51-40-05 FIG 2 AND 53-80-03-01 FIG PG 3.
MAIN DECK L5 DOOR FWD NR 4 STOP FTG FOUND CORRODED. L5 DOOR FWD NR 4 STOP FTG, PN 65 B08944-9, REPLACED IAW SRM 51-10-02 & FASTENERS INSTALLED IAW SRM 51-40-02.
STATION 1700 & STRINGER 41L & SKIN DENT. STATION 1690 - 1710, STRINGER 39L - 42L, SKIN DENT AREAS REPAIRED IAW RRI 53 - 61 - 11264 REV A.
LEFT BS 2598 FWD INNER CHORD, UPPER SPLICE FTG WAS ONE EACH HOLE CRACKED, APPROX 1/16". REPAIRED IAW R1-53-83-11266.
LEFT BS 1480, LONGERON EXTENSION FTG FOUND CRACKED APPROX 3/8" IN LENGTH. REPAIRED IAW SB 747-53A-2860 R1 & EO 4453A818 PART 3.
RIGHT BS 1480, LONGERON EXTENSION FTG FOUND CRACKED, APPROX 1/2" IN LENGTH. REPAIRED IAW EO 453A818 PART 4 & SB 747-53A 2860 R1.
FS 48, STATION 2658, RBL 34-38, WL313, BULKHEAD WEB CRACKED. REPAIRED IAW R1-53-83-11265 REV A.
RIGHT WING ILES 630 SEAL RIB INBD & LE & STIFFENER LOWER FOUND CRACKED. REPAIRED IAW RI-57-24-11273 REV A.
RIGHT WING NR 21, VC FLAP FOLDING NOSE SKIN DENT. REPAIRED IAW NR RI-57-44-11269 REV A.
MAIN DECK L5 BS 2230, BETWEEN STRINGER 22 & 23, FWD CUT OUT FOUND CRACKED. REPAIRED IAW SRM 53-60-152R-3 REPAIR 3.
LEFT BLG INBD STRUT DOOR INNER SKIN FOUND CHAFING MARK. REPAIRED IAW RI 52-80-11263 REV A.
DURING WALK AROUND, CHECK FOUND PIECE OF SKIN MISSING ON FUSELAGE, STATION 2638 - 2658, BL 310 RT, TEMPORARY REPAIR MADE ON FUSELAGE SKIN IAW EO 4453B153, 4453B154 & 4453B155 ALL PART 1.
CARGO DET 12 MAIN DECK, RESULTED IN FIRE MAIN DECK AFT. EICAS WENT OUT ON DECENT. BACKGROUND COLOR. INSPECTED MAIN DECK CARGO COMPARTMENT LINERS FOR OBVIOUS DAMAGE. IAW AMM TASK 25-59-01, FOUND NO ABNORMALITIES. OK FOR SERVICE. MCC WILL MAKE SDR DUE TO FALSE FIRE WARNING.
FIRE MAIN DECK AFT EICAS. FOUND FIRE DET LOOP 12B FAILED IN CMCCFDC UNITS 12B & 13B IAW AMM 26-14-01 PN 2156-756A SN 13473B IN POS 12B SN 12448B INSTALLED AT 13B. CFDC UNITS 12A & 13B PLACED ON DMI IAW 26-14-01-02 MEL MDDR 51415.
SUPRNMRY OXY ON EICAS. RESET SUPRNMRY SYS IAW AMM 35-00-00 EICAS MSG CLEAR, CHECKED OK.
CABIN STATION 1200, RBL 98 - 127 FLOOR INTERCOSTAL WEB FOUND CRACKED. R & R CABIN STATION 1200, RBL 98 - 127 FLOOR INTERCOSTAL WEB IAW R1-53-41-10462.
CABIN STATION 1180, LBL 98 - 127 FLOOR INTERCOSTAL WEB FOUND CRACKED. R & R CABIN STATION 1180, LBL 98 - 127 FLOOR INTERCOSTAL WEB IAW R1-53-41-10463.
DAMAGE WAS FOUND NEAR TAIL JACK AREA AT BS 2594, ABOVE STRINGER 42R. DAMAGE WAS FOUND TO BE BEYOND THE LIMITS OF SRM 53-00-01, FIG 101 ALLOWABLE DAMAGE. EO 4453A930, FAA 8110-320 DEC13 & NBSP PART 1 ALLOWS FOR A TIME LIMITED REPAIR & NBSP IAW & NBSP SRM 53-80-01, FIG 202 REPAIR 2. REVISION 1 OF & NBSP EO 4453A930 & FAA 8110-3 20 DEC13 IS ISSUED TO DOCUMENT DEVIATIONS OF THE REPAIR ACCOMPLISHED IN PART 1 & ADDING A PART 2 TO ACCOMPLISH CATEGORY A PERMANENT REPAIR IAW THE SRM 53-80-01, FIGURE 202 REPAIR 2 AT THE NEXT C CHECK.
OVEN STARTED SMOKING DURING USE. DISCONTINUED AND BREAKERS PULLED.
POST FLIGHT WALK AROUND INSPECTION, FOUND NR 4 T/E FLAP TRACK FAIRING DAMAGED BY FLAP DRIVE CRANK. FURTHER INSPECTION FOUND THE CAM DRIVE DETACHED FROM MID-FLAP. LT MID-FLAP ASSY AND NR 4 T/E FLAP TRACK FAIRING WAS REPLACED AND RIGGED IAW AMM 27-51-01 AND AMM 27-51-20.
FOUND LIGHTNING STRIKE DAMAGE TO THE NR 2 ENG LT THRUST REVERSER TRANSLATING COWL. DAMAGE ON THE T/E. A TIME LIMITED REPAIR WAS ACCOMPLISHED AS DESCRIBED IN PART 1 OF EO 4478A233 AND FAA 8110-3.
AFTER GEAR RETRACTION, EICAS MESSAGE, "GEAR DOOR" SYNOPTIC INDICATED LT MAIN GEAR DOOR NOT CLOSED, DUMPED FUEL AND RETURNED TO DEPARTURE. GROUND CHECK LOWER ACTUATOR; FLEX HOSES HAD NO PRESSURE UP. WING GEAR DOOR SEQUENCE VALVE REPLACED; RIGGED IAW MM 32-32-02-404-006, WING GEAR DOOR RETRACT ACTUATOR & OPS CHECKED NORMAL AND PERFORMED MLG RETRACTION TEST IAW MM 32-32-00; ALL NORMAL.
DURING MX WALK AROUND, MAINTENANCE FOUND THE FAN CASE ACOUSTICAL LINER PUNCTURE ON THE NR 3 ENGINE ESN 704925. MX DEFERRED ITEM IAW AMM 72-32-00, TABLE 602 ( OVER-SERVICEABLE-LIMIT EXTENSION), DAMAGE MUST BE REPAIRED WITHIN 10 FLIGHT CYCLES OR 100 FLIGHT HOURS, WHICHEVER COMES FIRST. DISPOSITION IS TO REMOVE ALL LOOSE PARTICLES; CLEAN THE REPAIR AREA WITH SOLVENTS AND FILL THE DAMAGE WITH THE EA934NA ADHESIVE; PERMANENT REPAIR WILL BE PERFORMED ON THE NR 3 ENGINE FAN CASE ACOUSTICAL LINER PUNCTURE WITHIN 10 FLIGHT CYCLES AFTER PART 1.)
NR 3 ENGINE INTAKE OUTER LINER SEGMENT AT 12 O'CLOCK POS, MINOR DAMAGE SIZE .5 X .5". ACCOMPLISHED EO 4472A095, PART 1 TIME LIMITED REPAIR IAW AMM 20-60-07.
DURING PREFLIGHT INSPECTION FOUND A HOLE IN THE FUSELAGE SKIN ABOVE THE LT BODY GEAR APPROX SIZE 1" X 3". ACCOMPLISHED TIME LIMITED REPAIR IAW E/O 4453A736.
LOW SPEED RTO BELOW 40 KTS DUE CONFIG WARNING "CONFIG GEAR CTR" BODY GEAR VERIFIED LOCKED IAW DDG REQ. R & R LT MLG ACTUATOR OPS CHECKED OK.
BODY GEAR STEERING INOPERATIVE. ACTUATORS ARE VERIFIED LOCKED AND SYSTEM DEACTIVATED. R & R MLG ACTUATOR.
RTO DUE TO TAKE OFF WARNING. "CONFIG GEAR CTR". IAW AMM 32-53-16. STEERING SYS CHECK FOUND LT AND RT BODY GEAR STRNG RT WORK INTERMITTENT BY BITS SHOW IN CMC AND PHYSICAL CHECK ON THE ACTUATORS. THE ECU WAS REPLACED AND TESTED. FOUND MESSAGE 32055, LBG STEERING LT ACTUATOR UNCOMMANDED EXT. AMM 32-53-04. LP 468786 M4. REPLACED ACTUATOR.
LEFT INBD MID FLAP T/E OF COVE PANEL DEFORMED IN FOUR PLACES. OPEN
NR 1 CORE COWL SCRATCH. REPAIRED IAW SRM 54-45-01-2R-1, REPAIR 1.)
CRACK DAMAGE IN SKIN AT BS 983, S 38L IN THE DRAG SPLICE FITTING AREA. CRACK DAMAGE WAS DETECTED DURING C3 CHECK WHILE ACCOMPLISHING INSPECTION IN COMPLIANCE WITH SB 747-53A2444, REV 2, AD 2001-22-04 IAW EO 4453A499. PERMANENET REPAIR DOUBLERS WERE INSTALLED IAW SRM 53-20-01, REPAIR 2, FIG 201.
ENGINE NR 4 FAIL. NORMAL PARAMETERS DURING TAKEOFF AND INITIAL CLIMB. ROLLED BACK TO IDLE ABOUT 20,000 FT. FAIL DURING DESCENT. AIR TURN BACK. WINDMILLED ABOUT 40 MINUTES. FOUND FUEL LEAK AT FUEL OUT CONNECTION AT FCOC GASKET.
UPON LANDING, CREW REST SOM L/E EICAS MESSAGE DISPLAYED ACCOMPLANIED BY SMOKE ODOR. NO VISIBLE SMOKE, PERFORMED "SMOKE OR FUMES IN CABIN, SOURCE UNKNOWN INSPECTION IAW FIM TASK 21-00 AND FOUND BURNED LIGHT BULB. NO OTHER DEFECTS NOTED. REPLACED LIGHT BULB IAW MM AND OPERATES OK.
DURING D2-CHECK, A DENT WAS FOUND ON LT FUSELAGE SKIN AT BS 1700, S-41L. THE DENT WAS BEYOND THE ALLOWABLE LIMIT IAW SRM 53-00-01, FIG 101. HFEC INSPECTED DAMAGED SKIN TO ENSURE FREE OF CRACKS IAW NDT MANUAL PN 6 51-00-00 FIG.23. HFEC INSPECTED THE OPEN HOLES TO ENSURE FREE OF DEFECT IAW NDT MANUAL PN 6 51-00-00 FIG.16. ENSURED THE DENT IS SMOOTH AND FREE FROM SHARP CREASES AND GOUGES. ENSURED NO FASTENER SHEARED OR LOOSEN IN THE DENT AREA. DENT DAMAGE MEASURED AS 5.3" (L) X 2.3" (W) X 0.040" (DEPTH).
R21 WING OTBD AFT FLAP NR 688JT GOUGED AT WBL 689.05. (PENDING)
PANEL NR 688IT OF RT OTBD AFT FLAP INNER SKIN DISBOND, WBL 747.678 RT, WBL 799.20 RT (REPAIR IAW NR T2011A57B-624)
NR 3 ENGINE PYLON PANEL NR 472QR BOLT HOSE WORN. (REPAIR IAW EGAT EZ T2P011A54B-688)
L/T LONGERON BOX FAIRING CRACK. (REPAIR IAW SRM 51-70-07, REV 58)
RT LONGERON BOX FAIRING CRACK. (REPAIR IAW SRM 51-70-07, REV 58.)
NR 2 ENGINE PYLON PANEL NR 462QR BOLT HOLES WORN. (REPAIR IAW EGAT E2 NR T2Q11A54B-687)
DENT ON THE FUSELAGE SKIN AT STA 1700 S-41L. (IAW T2011A53B-592, REV 00, INSP DENT AREA.)
DURING D2 CHECK INSP BEING PERFORMED; A DISBOND DAMAGE WAS FOUND TO THE RT WING OTBD T/E AFT FLAP UPPER PANEL INNER SKIN. DELAMINATION AREA WAS BETWEEN WING STATION, WBL 747.678 - 799.20 AND AS SHOWN IN FIGURE 2. (ALL DETAILS OF DAMAGE AND REPAIR DATA WERE REPORTED IN SR 1-1832155217. EGA ACCOMPLISHED REPAIR WITHOUT DEVIATION IAW PROPOSED STEPS IAW EGA-TLS-11-0036-04B DATED 25 MARCH 2011. ISSUED A SIGNED FAA FORM 8100-9 ON 25 MARCH 2011 AS AN APPROVAL.)
DURING D-CHECK INSP, CRACKS WERE FOUND ON SEAT TRACK AT BS 995. THE DAMAGED SEAT TRACK WAS REPAIRED IAW SRM 53-00-52-2R-13, FIG 201.
CRACK ON AFT FRAME OF NR 4 ENG LT CORE COWL. (REPAIR IAW T2011A71B-635, REV 00)
CRACK ON AFT FRAME OF NR 3 ENGINE LT CORE COWL. (REPAIR IAW NR T2011A71B-634, REV 00)
CRACK - SEAT TRACK UNDER FLOOR OF MAIN CARGO COMPT STA 995 LBL 76. (REPAIR IAW SRM 53-00-52-2R-13, REV 58)
DENT AND CRACK DAMAGE ON THE RIB OF LT WING OTBD T/E AFTER FLAP AT WBL 549.935. (REPAIR IAW EI NR. T2011A57B-597, REV. 00.)
CRACK-SEAT TRACK UNDER FLOOR OF MAIN CARGO COMPT, STA 995, RBL 76. (IAW SRM 53-00-52-2R-13, REPAIR 13, FIG 201, REV 58 FOR REPAIR.)
CRACK ON THE INTERCOSTAL OF BULK CARGO COMPARTMENT AT STATION 2040 RBL 38.525.(REPAIR IAW EI NO. T2011A53B-686 REV. 00.)
CRACK ON THE INTERCOSTAL OF BULK CARGO COMPARTMENT AT STA 2060, RBL 7.625. (REPAIR IAW EI NR. T2011A53B-685, REV 00.)
1 FASTENER HOLE WORN OUT ON NR 3 STRUT. ENG-TO-WING FAIRING ACCESS PANEL 472 EL. (REPAIR IAW E NR T2011A54B-563, REV 00 AND REV. 01.)
CRACK ON 65B23601-5 RIB OF LT HST L/E FAIRING LWR SIDE AT STA 145.01.0. (REPAIR IAW T2011A55B-61.4, REV 00; 01)
CRACK ON AFT FRAME OF NR 1 ENGINE LT CORE COWL. (REPAIR IAW NR. T2011A71B-675, REV. 00.)
CRACK ON THE CHORD OF LT WING FIXED T/E LOWER SUPPORT STRUCTURE AT WS 1185.40. (REPAIR IAW NR T2011A57B-615, REV 00 AND REV 01)
CRACK ON 65B23601-7 RIB OF LT HST L/E FARING LWR SIDE AT STA 151.543. (REPAIR IAW T2011A55B-611, REV 00; 01)
CRACK ON 65B23601-9 RIB OF LT HST L/E FARING LWR SIDE AT STA 159.109. (REPAIR IAW T2011A55B-612, REV 00; 01)
CRACK ON 65B23604-7, RIB OF LT HST L/E FARING LWR SIDE AT STA 441.753. (REPAIR IAW T2011A55B-613, REV 00; 01)
CRACK ON 65B23604-21, RIB OF RT HST L/E FARING LWR SIDE AT STA 501.359 (REPAIR IAW T2011A55B-614, REV 00; 01)
CRACK ON 65B23604-29 RIB OF LT HST L/E FAIRING UPPER SIDE AT STATION 535.734. (REPAIR IAW T2011A55B-619, REV 00 AND REV 01.)
CRACK ON 65B23601-5 RIB OF LT HST L/E FAIRING LOWER SIDE AT STA 145.011. (REPAIR IAW NR T2011A55B-620, REV 00 AND REV. 01.)
CRACK ON 65B23601-7 RIB OF LT HST L/E FAIRING LOWER SIDE AT 151.543. (REPAIR IAW NR T2011A55B-621 REV. 00 AND REV. 01.)
CRACK ON 65B23604-23 RIB OF LT HST L/E FAIRING UPPER SIDE AT STA 510.103 (REPAIR IAW T2011A55B-616, REV 00; 01)
CRACK ON 65B23604-27 RIB OF LT GST L/E FAIRING UPPER SIDE AT 51A 527.190. (REPAIR - IAW EI T2011A55B-618 REV 00, AMP; REV 01)
CRACK ON 65B23604-25 RIB OF LT HST L/E FARING LWR SIDE AT STA518.646. (REPAIR IAW T2011A55B-617, REV 00; 01).
CRACK ON 65B23604-12 RIB OF RT HST L/E FAIRING LWR SIDE AT STA 458.841. (REPAIR IAW T2011A55B-603, REV 00 ; 01)
CRACK ON 65B23604-10 RIB OF RT HST L/E FAIRING LWR SIDE AT STA 450.297. (REPAIR IAW T2011A55B-602, REV 00; 01)
CRACK ON 65B23604-8 RIB OF RT HST 4E FAIRING LWR SIDE AT STA 441.753. (REPAIR - IAW T2011A55B-601, REV 00 ; 01)
FOUND EXTERNAL SKIN HAD DENT AT AFT CARGO DOOR; AFT & AMP; LWR SIDE. STA 1914 TO STA 1918 (REPAIR - IAW EI T2011A52B-565, REV 00 & AMP; REV 01)
FOUND BULK CARGO DOOR OUTER SKIN HAD DENT AT STA 1994 L X W X D = 1" X 0.6" X 0.031" (REPAIR - IAW SRM 52-00-01-2R-9, REV 58.)
CRACK - CRACK ON 65B23604-22 RIB OF RT HST L/E FAIRING LWR SIDE AT STA 501.559. (REPAIR IAW T2011A55B-605, REV 00; 01)
CRACK ON 65B23604-24 RIB OF RT HST L/E FAIRING LWR SIDE AT 510.103. (REPAIR IAW T2011A55B607, REV 00; 01)
CRACK ON THE FOLDING NOSE SKIN OF LT WING NR 10 VC FLAP OTBD EDGE AT ILES 779.50.
CRACK ON 65B23604-26, RIB OF RT HST L/E FAIRING LWR SIDE AT STA 518.646. (REPAIR IAW T2011A55B-608 REV 00; 01)
CRACK ON 65B23604-26 RIB OF RT HST L/E FARING LWR SIDE AT STA ;527.190 (REPAIR IAW T2011A55B-608, REV 00; 01)
DENT - FWD BULK CARGO DOOR OUTER SKIN HAD DENT AT STA 1994 L-1", W-0.6", D-0.031". (IN PROCESS).
DENT- FWD EXTERNAL SKIN HAD A DENT AT AFT AND LOWER SIDE, STA 1917 TO 1918 (IN PROCESS).
CRACK - CRACK ON 65B23604-14 RIB OF RT HST L/E FAIRING LWR SIDE AT STA 467.384. (REPAIR IAW T2011A55B-604, REV 00; 01)
FOUND EXTERNAL SKIN HAD DENT AT AFT CARGO DOOR FWD; LWR SIDE, STA 1812 TO STA 1815. (REPAIR - IAW EI T2011A52B-564, REV 00 ; REV 01)
FOUND EXTERNAL SKIN DENTED AT FWD CGO DOOR AFT; LWR STA 670. (REPAIR IAW SRM 52-30-01-2R-2, REV 58).
DENT FWD EXTERNAL SKIN HAD DENT AT AFT CGO DOOR FWD AND LOWER SIDE. STA 1812 TO STA 1815 (OPEN)
DURING U/D SERVICE DOOR SLIDE DEPLOYMENT TEST FOUND SLIDE AUTOMATIC AND MANUAL DEPLOY FUNCITONAL FAIL. (OPEN)
FWD EXTERNAL SKIN DENTED AT FWD CARGO DOOR AFT AND LOWER SIDE STA 670. REPAIRED FWD CARGO DOOR SKIN IAW SRM 52-30-01 REPAIR 2 FIGURE 201 SHEET 10 REV 58.
CHAFING DAMAGE ON THE NR 1 ENG NACELLE STRUT INBD AFT SIDE OF FR ACCESS DOOR ASSY. (REPAIR IAW EI T2011A54B-536, REV 00)
DURING TAXI, ENROUTE FOR TAKEOFF. ACFT CAME IN CONTACT WITH ANOTHER ACFT ON THE TAXI WAY. THE WINGLET WAS DAMAGED. (REMOVED WINGLET AND DISPATCHED IAW CDL 57-28-1).
DURING WALK-AROUND , MX FOUND DAMAGE TO THE RT WING OTBD FORE AND AFT FLAPS (REF FIG 1-3).DIMENSIONS AND DETAILS: RT OTBD FORE FLAP WBL793 - L/E PUNCTURE - 2.250 IN. X 2.0 IN. (REF FIG 1). RT OTBD FORE FLAP WBL810 - L/E PUNCTURE - 5.0 IN. X 2.5 IN. (REF FIG 2). RT OTBD AFT FLAP WBL738 - T/E - LOWER SURFACE DELAMINATION - 5.0 IN. DIAM. (REF. FIG 3). PERMANENT REPAIRS ACCOMPLISHED IAW THE SRM 57-53-01, FIGURE 201, REPAIR 1 TABLE I. THE REPAIRS ACCOMPLISHED IN PART 1 OF THIS EO ARE CATEGORY A PERFORMED IAW THE SRM 57-53-01, FIGURE 201, REPAIR 1, TABLE I.
DURING A-CHECK AND INSP IAW EO 4452A068, WEAR WAS FOUND IN THE MAIN DECK SIDE CARGO DOOR MIDSPAN LATCH CAM THAT IS OUTSIDE OF WEAR LIMITS IAW THE AMM 52-32-01-206. FWD MID SPAN LATCH CAM ID= 1.1740 , ALLOWED WEAR LIMITS IAW AMM IS 1.1240 (0.05). AFT MID SPAN LATCH CAM ID= 1.1445 , ALLOWED WEAR LIMITS IAW AMM IS 1.1240 (0.02). ACFT SCHEDULE PREVENTED REPLACEMENT OR REPAIR IAW THE OHM 52-36-75, SO THIS EO ISSUES A TEMPORARY REPAIR WHICH IS FAA APPROVED IAW DER (DERT710167-SW) VIA FAA FORM 8110-3 DATED 10OCT2010. PART 1 OF THIS EO DOCUMENTS THE WEAR OF THE FWD CAM AND THE AFT CAM OUTSIDE OF WEAR LIMITS IAW AMM 52-32-01-206. THE WEAR AREA IS CLEANED UP AND PRIMED AS A TEMPORARY REPAIR. PART 2 OF THIS EO WILL INSPECT THE CAMS BEFORE EACH FLIGHT FOR ADDITIONAL WEAR AND TO VERIFY THAT NO ADDITIONAL DAMAGE HAS OCCURRED AND TO TOUCH UP ANY DAMAGE PRIMER. PART 3 OF THIS EO WILL REPLACE THE DAMAGE CAMS OR REPAIR THEM IAW THE OHM.
EO 4425A197; DURING MX WALKAROUND, MX FOUND THE MAIN DECK - RT BS1250, WL 248 SIDEWALL PANEL DAMAGED; HOLE 2.5 IN. LONG X 1.5 IN. WIDE. (IAW AMM 25-52-01-308-062, THE DAMAGE/HOLE IS OUT OF LIMITS. DISPOSITION WAS MADE TO PERFORM A TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, DVI INSPECTIONS AFTER EVERY 5 FLIGHT CYCLES UNTIL ACCOMPLISHMENT OF PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1.)
EO 4452A084 DURING WALKAROUND INSP, MX FOUND THE CARGO DOOR OUTER SKIN WITH DENT/SCRATCH DAMAGE, MEASURES: 2.0 IN LONG X 1.5 IN WIDE X 0.125 IN DEEP. THE DENT IS OUT OF LIMITS IAW THE SRM 52-30-01, FIG 101, DETAIL XI, ALLOWABLE DAMAGE 1. THE BULK CARGO DOOR OUTER SKIN IS MADE FROM 0.062 CLAD 2024 T-3 (REF. DWG 65B04514). (DISPOSITION WAS MADE TO PERFORM TIME LIMITED REPAIR AS DESCRIBED IN PART 1 WORK INSTRUCTIONS, INITIATE REPEAT INSP AT EVERY 25 FC (FLIGHT CYCLES) AND SCHEDULE PERMANENT REPAIR PRIOR TO THE ACCUMULATION OF 1,000 FH (FLIGHT HOURS) AFTER PART 1. PART 1 OF THIS EO ACCOMPLISHED TIME LIMITED REPAIR AND IS APPROVED BY DER (DERT-710167-SW) VIA FAA 8110-3 FORM ISSUED 01SEP10 SINCE THE DAMAGE EXCEEDS THE ALLOWABLE DAMAGE LIMITS IAW SRM 52-30-01, FIG 101, ALLOWABLE DAMAGE 1.)
ON WALKAROUND FOUND NR 4 TIRE RECAP SEPARATED FROM TIRE. PERFORMED AIRCRAFT INSPECTION PER CHAP 5-51-34-201. REPLACED TIRE PER AMM 34-45-01. AIRCRAFT INSPECTION REVEALED SEVERAL DENTS TO LEFT I/B LOWER SURFACES OF FORE, MID AND AFT FLAPS AND TRAILING EDGE PANEL. EO 4457A239 COVERS INTERIM REPAIRS AND REPETITIVE INSPECTION CYCLES FOR CONTINUOUS SERVICE TILL PERMANENT REPAIRS CAN BE ACCOMPLISHED AT NEXT C CHECK. FOREFLAP WAS REMOVED AND ROUTED TO SHOP TO EXPEDITE REPAIRS. FOREFLAP REMOVED/INSTALLED PER AMM 27-51-02-404-011. OPS CHECK NORMAL.
RT OTBD ELEVATOR L/E INBD BALANCE WEIGHT BOX ANGLE CRACKED. ELEVATOR STA 227.65 SUPPORT WEB AND WEB ANGLE REPLACED IAW SRM 51-10-02 AND INSTALLED IAW 51-40-02.
LT INBD ELEVATOR L/E MOST INBD RIB ANGLE CRACKED. INBD RIB UPPER MOST UPPER RIB ANGLE BRACKET REPLACED IAW SRM 51-00-02 AND 51-40-02.
LT WING INBD MIS FLAP TRACK CARRIAGE FITTING SAFE LINK ATTACH BOLT BORE HOLE CRACKED. LT WING INBD MID FLAP REPLACED IAW 27-51-01.
LT WING LOWER SURFACE ADJACENT TO NR 5 SPOILER OTBD AREA UPPER SURFACE FIXED PANEL SUPPORT STRUCTURE CRACKED. UPPER SURFACE SUPPORT FITTING REPLACED IAW SRM 51-10-02, 51-40-02 AND AMM 57-22-01.
FLEXIBLE ELECTRICAL CONDUIT AT THE LT WING GEAR DAMAGED. "PERFORMED A TIME LIMITED REPAIR IAW THE SWPM 20-10-91".
DENT ON OUTBOARD AFT FLAP NOSE AND MID FLAP DUE TO OUTBOARD FLAP FITTING FAILURE. REPAIRED PER SRM 51-70-17. REPLACED SUPPORT ARM.
MAIN DECK CARGO COMPARTMENT RT AFT SIDEWALL CRACKS FOUND ON FRAME INNER FLANGE AT STA 1740 AND 1780. JUST ABOVE FRAME SPLICE AT BETWEEN STRINGER 11R AND 12R. REPAIRED IAW EO 4463A178. (K)
DURING CRUISE, EICAS ADVISORY "HYD PRESS ENGINE 1" ON HYD SYNOPTIC. NR EDP AND DEMAND PUMPS RUNNING. THEN NOTED EDP INTERMITTENT AND IAW CHECKLIST EDP SWITCH OFF, BUT PUMP DID NOT SWITCH OFF. (EDP CONTINUED RUNNING INTERMITTENTLY AND DEMAND PUMP RUNNING). LATER NOTICED THAT "EDP PRESS 1 CIRCUIT BREAKER WAS POPPED. ATTEMPTED RESET BUT C/B POPPED AGAIN. AFTER CONSULTING WITH MCC AND DISPATCH, DIVERTED. FOUND AND REPAIRED CHAFED WIRING AT EDP, DEPRESSURIZATION SOLENOID CONNECTOR IAW WDM 29-11-01. NR 1 SYSTEM DEPRESSURIZATION SOLENOID CIRCUIT BREAKER RESET AND OPERATIONS CHECKED OKAY IAW 29-17-00. (K)
LOUD BANG FOLLOWED BY RAPID RISE IN CABIN ALTITUDE WITH "CABIN ALT" EICAS MESSAGE. FOUND NR 1 PACK DUMP VALVE AT FAULT. DEACTIVATED VALVE IN CLOSED POSITION. TRANSFERRED TO MEL M08-058 REF MEL 21-51-10 CAT C.
AFTER TAKEOFF UNABLE TO PRESSURIZE AIRCRAFT. FOUND CONDITIONED AIR CHECK VALVE CRACKED AND FOUND HOLE ON FORWARD CARGO COMPARTMENT AIR SUPPLY DUCT. REMOVED AND REPLACED CHECK VALVE AND ACCOMPLISHED LEAK CHECK IAW 21-28-08. AIR DUCT REMOVED AND FORWARDED FOR REPAIR TO AVDUCT. RE-INSTALLED DUCT, LEAK CHECKED IAW 21-23-02. NO ABNORMALITIES.
ABORTED TAKEOFF DUE TO ENGINE 4 REVERSER EICAS MESSAGE APPEARED AT 70 KNOTS ON TAKEOFF ROLL. REJECTED TAKEOFF EICAS MESSAGE REPLACED WITH STATUS MESSAGE. DEACTIVATED THE REVERSER AND PLACED ON DMI PER MEL 78-31-01.
LT INBOARD T/E AFT FLAP REPAIR ALUMINUM FOIL (SPEED TAPE) PEELING FROM CENTER OUTWARDS APPROX 12 INCHES OUTBOARD OF THE NR 4 CANOE FAIRING FACE AND 1 INCH FWD OF THE AFT EDGE. ALUMINUM FOIL (SPEED TAPE) REPLACED AS PER PART 2 OF WORK INSTRUCTIONS FOE INITIAL AND REPEAT INSPECTIONS DETAILED IN EO 4457A102.
RIGHT T/E AFT FLAP REPAIR SIX INCHES FWD OF THE TRAILING EDGE AND 18 INCHES OUTBOARD OF THE OUTBOARD FACE OF NR 5 CANOE FAIRING HAS SIGNS OF DETERIORATION AND WATER INGRESS OVER AN AREA APPROX 1 INCH DIAMETER. PERMANENT REPAIR CARRIED OUT IAW SRM 57-53-01. VACUUM PRESSURE AND HEAT APPLIED AT 26 INCHES OF MERCURY AND 250 DEGREES.
RIGHT INBOARD TRAILING EDGE FLAP (AFT) COMPOSITE STRUCTURE HAS PUNCTURE IN IT APPROX 1 INCH IN LENGTH ABOUT 13 INCHES INBOARD OF OUTBOARD FACE OF NR 5 CANOE FAIRING. PERMANENT REPAIR CARRIED OUT IAW SRM 57-53-01 AND XEO 57-122807.
RIGHT WING GEAR GULL WING DOOR FORWARD EDGE DELAMINATED. DELAMINATION REPAIRED IAW SRM 52-80-02 AND XEO 57-092907-1.
NR 3 ENGINE RIGHT T/R TRANSLATING COWL LOWER FAIRING HAS A CRACK APPROX 3.0 INCHES AT THE FORWARD SECTION AND RIVETS PULLING THROUGH AT THE AFT SECTION. RIVETS REPLACED IAW SRM 51-40-02. AN INTERIM REPAIR WAS DONE TO THE CRACKED FAIRING BY STOP DRILLING AND INSTALLING AN EXTERNAL DOUBLER IAW XEO 78-092607.
RIGHT INBOARD T/E FLAP AFT FLAP LOWER SURFACE HAS VARIOUS NICKS. INTERIM REPAIR CARRIED OUT IAW SRM 57-53-01, AND XEO 57-092607.
LEFT WING T/E FLAP INBOARD AFT FLAP LOWER SURFACE HAS VARIOUS NICKS AND SCRATCHES. INTERIM REPAIR CARRIED OUT IAW SRM 57-53-01, AND XEO 57-092607.
TOP OF FLOOR WEB DAMAGED AT STA 1660-1680 IN AFT LOWER CARGO COMPARTMENT. REPAIRED PER XEO 53-080707 AND PER BOEING SRM 51-70-13 FIG 201 REPAIR 1.
FLAP DRIVE MESSAGE. OUTBOARDS AT 30 INBOARDS 25. LE ALL GREEN. RT INBOARD FLAPS INDICATES EXTENDED MORE THAN LEFT INBOARDS. FOUND NR 4, 5 AND 6 JACKSCREWS/BALLSCREWS HAD PLAY AND WERE WORN REMOVED AND REPLACED ALL 3 UNITS OPS CHECKED OKAY.
CREW REPORTED SLIGHT SMOKE IN THE COCKPIT DURING PRE-FLIGHT OPS. MAINTENANCE SHUT DOWN AIRCRAFT POWER. AFTER POWER SHUT DOWN, INSPECTED COCKPIT FOR SMOKE OR DAMAGE. NONE NOTED. INSPECTED E/E BAY AND MAIN DECK NO SMOKE NOTED. TURNED POWER BACK ON FOR AN HOUR. NO SMOKE OR SMELL NOTED. CREW PRE-FLIGHT COMPLETED WITH NO ISSUES. VERIFIED THAT NO C/B'S ARE OUT AND NO STATUS MESSAGES.
ELECTRICAL BURNING SMELL ON TAXI IN, E/E BAY. AFTER DEBRIEF, STS EE CLNG SUP FAN APPEARED. NIL STOCK. ITEM TRANSFERRED TO DEFERRED DMI M06-032 PAGE 63427 PER MEL 21-58-06. CAT "C", PART ON ORDER.
AIR TURN BACK. STATUS MESSAGE: ENG 3 FUEL FILTER. THE AIRCRAFT RETURNED TO DEPARTURE. REMOVED AND REPLACED FUEL FILTER IAW MM, LEAK CHECKED SATISFACTORY. (K)
FLIGHT CT 603, PIK-LUX 08 JAN, 2005 - IB LOG ITEM, LT OB MID FLAP PANEL DELAMINATED. MAINTENANCE PICK-UP ITEM. DURING FLAP REPLACEMENT FOUND IB CARRIAGE ASSY CORRODED. (LEVEL 1) REPLACED LT OB MID-FLAP, MM 27-51-04, REF LOG PAGE 544103. REPLACED IB CARRIAGE ASSY MM 27-51-28, REF LOG PAGE 544105. MID FLAP PN 65B01925-311A, SN 000549; CARRIAGE ASSY 65B08027-53, SN BT1055V.
FLT 605 - JFK - REMOVED AND REPLACED RIGHT FMC PER MM 34-61-01. INSTALLED FMC SOFTWARE PER MM 34-61-00 SYSTEM, OPS CHECK NORMAL PER MM 34-61-60/501. (M)
GT603/6 HSV/PIK BURNT ODOR IN COCKPIT: AIRCRAFT HAS A BURNT ODOR DURING ENTIRE FLIGHT. TRACED TO TRANSFORMER T44, REMOVED AND REPLACED SAME IAW MM 33-11-05. NO CIRCUIT BREAKER AVAILABLE, ISOLATED WIRING AND TRANSFERRED TO DMI M04-014 IAW MEL 33-11-01 CAT C. CB WAS REMOVED AND REPLACED, AND OPERATION CHECK NORMAL.